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Method of controlling missile flight using attitude control thrusters

a technology of thrusters and missiles, applied in direction controllers, instruments, weapons, etc., can solve problems such as difficulty in using fins

Active Publication Date: 2011-11-15
RAYTHEON CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention is a method for controlling the flight of a missile by using thrusters to change its orientation. The method involves sensing the rate at which the missile's orientation is changing and making a decision to fire additional thrusters if the rate of change exceeds a certain threshold. This allows for smoother and more accurate flight control of the missile.

Problems solved by technology

Fins may be difficult to use, especially in situations where there is a short flight duration and severe changes in trajectory during flight.

Method used

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  • Method of controlling missile flight using attitude control thrusters
  • Method of controlling missile flight using attitude control thrusters
  • Method of controlling missile flight using attitude control thrusters

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Embodiment Construction

[0016]A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when the angular rate of change of the missile, or more broadly a factor based on the angular rate of change, exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions, to keep the missile from veering too far from the course established by the pitch over missile.

[0017]FIG. 1 shows a...

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PUM

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Abstract

A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.

Description

BACKGROUND OF THE INVENTION[0001]1. Technical Field of the Invention[0002]The invention is in the field of methods and devices for controlling missile flight.[0003]2. Description of the Related Art[0004]Methods of controlling missile flight of 360 degree capable rockets have often focused on using fins to steer the missile. Fins may be difficult to use, especially in situations where there is a short flight duration and severe changes in trajectory during flight.SUMMARY OF THE INVENTION[0005]According to an aspect of the invention, a method of controlling flight of a missile includes firing attitude thrusters when an angular rate is exceeded.[0006]According to another aspect of the invention, a method of controlling flight of a missile includes the steps of: sensing a rate of change of angular orientation of the missile; and if the rate of change of angular orientation of the missile exceeds a threshold angular rate change value, making a decision regarding firing one or more compen...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F42B15/01F42B10/66F42B15/00F42B10/00
CPCF42B10/661
Inventor KINSEY, JR., LLOYD E.COOK, JAMES M.
Owner RAYTHEON CO